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  • Life Sciences (General)  (1)
  • QUALITY ASSURANCE AND RELIABILITY  (1)
  • Spacecraft Design, Testing and Performance  (1)
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  • 1
    Publication Date: 2011-08-19
    Description: The concept of pressure proof testing of fuselage structures with fatigue cracks to insure structural integrity was evaluated from a fracture mechanics viewpoint. A generic analytical and experimental investigation was conducted on uniaxially loaded flat panels with crack configurations and stress levels typical of longitudinal lap-splice joints in commercial transport aircraft fuselage. The results revealed that the remaining fatigue life after a proof test was longer than that without the proof test because of crack growth retardation due to increased crack closure. However, based on a crack length that is slightly less than the critical value at the maximum proof test stress, the minimum assured life or proof test interval must be no more than 550 pressure cycles for a 1.33 proof factor and 1530 pressure cycles for a 1.5 proof factor to prevent in-flight failures.
    Keywords: QUALITY ASSURANCE AND RELIABILITY
    Type: Theoretical and Applied Fracture Mechanics (ISSN 0167-8442); 14; 101-116
    Format: text
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  • 2
    Publication Date: 2016-06-07
    Description: This viewgraph presentation gives an assessment of the state-of-the-art in the design and manufacturing of large component structures, including details on the use of continuous fiber reinforced polymer matrix composites (CFRP) in commercial and military aircraft and in space launch vehicles. Project risk mitigation plans must include a building-block test approach to structural design development, manufacturing process scale-up development tests, and pre-flight ground tests to verify structural integrity. The potential benefits of composite structures justifies NASA's investment in developing the technology. Advanced composite structures technology is enabling to virtually every Aero-Space Technology Enterprise Goal.
    Keywords: Life Sciences (General)
    Type: Proceedings of The 4th Conference on Aerospace Materials, Processes, and Environmental Technology; NASA/CP-2001-210427
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  • 3
    Publication Date: 2019-07-13
    Description: Cracks were detected in flow liners at the gimbal joints in the LH2 feedlines of the space shuttle's main engines. The cracks initiated at defects in the drainage slots of the flow liners and grew due to high cycle fatigue. Fracture mechanics analyses were conducted to evaluate the life of the liners. These analyses yielded extremely short lives in the presence of small surface or corner cracks. A high fidelity detection method, edge replication, was used to detect the very small cracks. The detected cracks were removed by polishing and the surface quality of the slots was reestablished to improve life of the liners.
    Keywords: Spacecraft Design, Testing and Performance
    Type: ICCES 2005 - International Conference on Computational & Experimental Engineering and Sciences; Dec 01, 2005 - Dec 06, 2005; Chennai; India
    Format: application/pdf
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